Abstract: To achieve automatic setting into coincidence, the following are provided: a mechanical tension elements arranged to act on an upstream member (9) substantially along the axis (X) along which approach elements (13) act, but in the opposite direction; elements (37) for constraining the member (9) in rotation with a mechanical angular guide element; and phase-shifter elements (47) for shifting the phase of the upstream member (9) relative to the downstream member (10) by sliding against a reference that is stationary in rotation relative to the downstream member (10).

Abstract: To achieve automatic setting into coincidence, the following are provided: a mechanical tension elements arranged to act on an upstream member (9) substantially along the axis (X) along which approach elements (13) act, but in the opposite direction; elements (37) for constraining the member (9) in rotation with a mechanical angular guide element; and phase-shifter elements (47) for shifting the phase of the upstream member (9) relative to the downstream member (10) by sliding against a reference that is stationary in rotation relative to the downstream member (10).

Abstract: A fabric comprising elongated steel elements is provided. This fabric is to be used to provide cut-resistance or reinforcement for protective textiles. Elongated steel elements are in contact relationship, so improving the resistance to knife cutting actions.

Abstract: A fabric comprising elongated steel elements is provided. This fabric is to be used to provide cut-resistance or reinforcement for protective textiles. Elongated steel elements are in contact relationship, so improving the resistance to knife cutting actions.

Abstract: Mechanical assembly for transmitting forces along an axis driven by a substantially axial movement in translation under the effect of a thrust load. This mechanical assembly comprises a transmitting part of the thrust load input movement and a receiving part of the thrust load output movement, said mechanical assembly comprising a detector for detecting the passing of a force threshold represented by a predetermined value of the thrust load, and including an elastic element and an indicator part arranged in such a way that when the thrust load exceeds the threshold value, the thrust load acts on the elastic element and modifies its axial dimension allowing the indicator part to move to the warning position.

Abstract: The control device is of the type including two annular disks (3,6), a rotating and non-rotating disk, assembled by at least one ball bearing (20) and mounted concentrically about the rotor shaft (1). The non-rotating disk (3) is mounted so as to oscillate with respect to the shaft (1) via a mechanism consisting of swivel/laminated articulations (2, 10). The mechanism for tilting, for axial displacement and for retention in rotation of the non-rotating disk includes two swivel joints (2) which are diametrically opposite on either side of the axis of rotation of the shaft (1) and are centered on the longitudinal tilting axis (A--A) of the non-rotating disk (3). Each swivel joint is retained between a disk support (5), which is mounted so as to slide parallel to the axis of the shaft (1) along a disk guide (4) which is itself coaxial with the shaft (1) and fixed about the latter, and an element (9) for fixing to the non-rotating disk (3).

Abstract: The invention provides an integrated hub-mast with a single piece tubular body which supports, by its hub body part (3), a reinforcing girdle (6) on each side of which openings (10, 11) are formed. For each blade of the rotor a retaining and pivoting member (13), formed preferably by a spherical stratified stop, is fixed to the girdle (6) and is retained in the hub body (3), and this member (13) is also fixed between the ends inside the hub body (3), of the lower (20) and upper (21) branches of a forked fastening part (19) connecting the blade to this member (13), these branches passing through the openings (10, 11) of a corresponding pair of openings. A heel (23) fixed under the lower branch (20) bears against a reciprocal ring (24) mounted on a support (29) in the hub-mast (1), which has external fastenings for coupling to resilient return and drag damping members of the blades.

Abstract: The flapping stop device of the invention is intended for a gyroplane rotor comprising a hub (3) to which each blade (22) is connected by retaining and pivoting members (16) having two frames, one (17) of which is fixed to the hub (3) and the other (19) of which, in an internal radial position with respect to the first one, is locked for movement with the root (23) of the blade (22). The internal frame (19) has, projecting radially inwardly, at least one nose piece (29) having a stop surface and defining a convex cylindrical sliding surface (28) on the internal radial face of the frame (19). The nose piece or pieces (29) and the convex surface (28) cooperate respectively with one or more bearing surfaces (34) and a complementary concave surface (33) of a central stop (30) integral with the hub (3) or with the rotor mast (2).

Abstract: The invention relates to a device incorporating retractable stops for limiting the flappings of the blades of the main rotor of a rotorcraft. Each lower stop comprises a convex roller presenting a convex stop surface and bearing a weight at the end of an arm. By its convex roller, the lower stop is mounted to pivot about the pin for retaining the blade on the hub. On the ground, the bearing member is in contact with a lower bearing surface fast with the blade at the level of the pitch control lever, in order to limit the downward flappings of the blade. The lower stop pivots about the pin above the lower plate. The upward flappings of the blade may be limited by upper stops disposed substantially symmetrically below the upper plate. A second lower weight, returned by a spring, and engaging by a nose-shaped element in a notch in the rear of the bearing surface, acts as upper stop. The invention is more particularly applicable to equipping helicopters.

Abstract: Apparatus for controlling both collective and cyclic pitch of blades of a helicopter rotor comprises a non-rotating plate which is connected via a fixed caliper and servo controls to a fixed housing and to which is attached the internal ring of a ball race bearing. The external ring of the bearing carries a rotating plate, which is connected by means of rotating caliper or links to each of the rotors and by means of pitch rods to control levers for adjusting the pitch of the blades. The non-rotating plate is fixed to external armatures of laminated joint pieces which are mounted slidingly up and down a guide base. The collective pitch is controlled by sliding the assembly of non-rotating plate and joint pieces up or down the guide base while the cyclic pitch is controlled by inclining the assembly relative to the main rotor shaft. This inclination involves deformations in the laminated joints.